Oil burner



s. M. HANSEN OIL BURNER May 31, 1932.

Filed Aug. 11'; 1927 2 Sheets-Sham'I l S. M. HANSEN oL BURNER vMay 31, 1932.

2 Sheets-Sheet 2 Filed Aug. 11V. 1927 Patented May 3l, 1932 UNITED STATES PATENT OFFICE SINIUS M. HANSEN, OF LYNN, MASSACHUSETTS, ASSIGNOR, BY MVESNE ASSIGNMENTS, p,

TO A T OIL BURNER CO., F LYNN, 'MASSACHUSETTS A CORPORATION OF MASSA- CHUSETTS OIL BURNER Application filed August 11, 1927. Serial No. 212,236.

This invention relates to oil burners and more particularly to that class of burners which are commonly known as rotary or turbine burners, and insome respects the present 5 application comprises a continuation .of my prior application Serial No. 44,7 7 7, filed July The present invention similarly provides a simple and highly efficient oil burner Which is 10 adapted to afford a clear burning flame due to the thorough vaporization of the fuel, the burner being provided with light, inexpensive component parts and having the moving elements thereof reduced to the utmost simplicity. This burner is designe-d to be adjustable in capacity so that it may be installed and operated in heaters of Widely varying sizes and with various types of fire boxes, thus permitting a burner of a given size to be capable of practical universal use and thus obviating the necessity of providing a series of sizes and styles of burners for use With different types of furnaces or heaters.

It is an object of the invention to provide at a 10W cost an oil burner of high eiiiciency and adaptability to various uses, Which has comparatively few moving parts, all of which are enclosed or protected with consequent avoidance of unnecessary tampering or in J jury to persons.

`Heretofore, it hasbeen usual to construct burners of this character -in Which the rotary means were mounted upon ball bearings F which have been lfound unsatisfactory due to noise, vibration, `and unreliability `under service conditions. `For example, the heat from the burneroften causes the cages of ball bearings to Warp oraffects the metal thereof so that sticking results, Even a slight impediment to rotation issufiicient to prevent starting ofthe rotary means in response to the air blast; thus enough oil may collect at the burner end to cause a serious explosion when the bearings fail to function With ease and reliability. Plain bearings have commonly been believed to be unsuitable for this purpose because of the difficulty of lubrication at the necessarilyihighbearing speeds, and due to the inability ofalburner-having plain bearings to besuificiently responsive-tov theinitial air blast to afford satisfactory vaporization` of the fuel upon starting.

The present invention is designed to obviate these difficulties and to utilize plain bearings of anti-friction material preferably provided with auxiliary lubricating means designed to divert a portion of the fuel oil for bearing lubrication. For these purposes the invention provides a more efficient arrangement of the necessary component parts of a burner of this type as Well as a more effective and scientific distribution of the material in these part-s. The spindle or shaft ofthe rotating means is so designed that the bearing speeds are comparatively low Whilecomparatively inexpensive yet accurate con-- struction. The rotating means accordingly has an unusually low moment of inertia s0 that its response to the action of the air blast is almost instantaneous; the fuel-receiving member accordingly rotates at a speed highv enough to ensure atomization ofthe oil as soon as the fuel has had time to flow to the burner tip. Thus any danger of the collection of a quantiay of unburnt oil in the vicinity of the burner tip is avoided so that there is no tendency to have an explosive effect, which maybe dangerous and is at least extremely objectionable.

The invention furthermore provides an oil burner of thischaracter in Which the rotary turbine means is arranged in a unit which may be quickly detached from the remainder of the oil burner in order to permit easy removal and replacement of the moving parts. Furthermore, the turbine means is longitudinally adjustable in relation tothe burner tip in order to adjust the flame to vary its shape to suit various kinds of heaters or furnaces,

`or to suit various qualities of fuel, the parts being so arranged that the adjustments may be made while the burner is operating.

The invention also provides a light fuelreceiving member or cup having passages adapted particularly to break up the fuel and to atomize it under action of centrifugal force and the air blast.

The above and further objects of the invention will be apparent to those skilled in the art upon a reading of the subjoined description and claims in conjunction with the accompanying drawings, in which Fig. 1 is a central longitudinal section'of the improved burner;

Fig. 2 is a section on line 2-2 of Fig. 1;

Fig. 3 is a top plan view of the burner tip portion of the assembly;

Fig. 4 is a section on line 4-4 of Fig. 1;

Fig. 5 is an elevational view of one of the turbine members;

Fig. 6 is an end elevation of the burner tip;

Fig. 7 is a view partly in section and partly in elevation of a portion of the burner cup; and

Fig. 8 is an edge view of the turbine.

Referring to the accompanying drawings, the improved burner is provided with an air conduit 1 which is adapted to receive a blast of air from any suitable source. Located at' the outer end of conduit 1 is the burner tip port-ion 2 which comprises an annular member of nozzle-like construction having an open outer end and preferably provided with the openings 3 disposed at an angle to the longitudinal axis of conduit 1. Preferably the conduit 1 may be mounted within a casting 4 provided with a flange 5 and a box-like extension 6,'the flange 5 being designed to be secured to the furnace or heater in which the burner is installed. The member 4 supports walls 7 which may be formed of lire clay or similar refractory material to form a combustion box around the end of the nozzle. A lateral extension of casting 4 supports the thermostatic regulator 8, which may be of any suitable design automatically to control operation of the burner. lt is to be understood that the design of the nozzle and the construction of the combustion box with its walls of refractory material 7 more particularly form the subject matter of copending application of Carl Olsen, Serial. No. 123,562, filed July 19, 1926, now Patent No. 1,681778, dated August 21, 1928. A suitable pilot, for example a gas burner 10, may extend through thecasting 4, having its end located adjoining the burner tip 2.

rlhe frame 20 is disposed within the conduit 1 andcomprises spider-like end portions 21 and 22, each of which includes a plurality of radial struts, the vertically disposed struts being connected by the longitudinal frame members 25, Figs. 1 and 4. These frame members and the ends of the horizontal struts slidably engage the inner surface of conduit 1. Mounted within the intermediate portions of the spider sections 21 and 22 are the plain bearings 27 and 28, respectively, these bearings preferably being formed of self-lubricating material such as a graphite bronze composition. Mounted in bearings 27 and 28 is the rotatable shaft or spindle 29 of the rotary means. Preferaby this shaft is of restricted diameter and has a shoulder 30 adjoining bearing 27 which is adapted to engage the spacer 31. The adjoining end of the shaft is threaded, as designated by numeral 32, to receive a nut 33 which holds a washer against the turbine unit 34, thereby clamping the same against the end of spacer 31. Spacer 31 engages the end of bearing sleeve 27 to provide a highly satisfactory bearing to receive the thrust resulting from impingement of the air upon the turbine. A tubular casing 0r distance member 26 surrounds shaft 29, between frame ends 21 and 22, having its ends juxtaposed to the ends of the bearing sleeves and serving to exclude dust from the same.

Preferably the turbine unit comprises a pair of sheet metal turbine members 35 in the form of fan-like propellers, each of which is struck out of a solid disk. One of these members is shown more particularly in Fig. 5 and has a central portion 36 adapted to engage shaft 29, with a plurality of struck out blades 37 havingtheir inner ends integral with portion 36 and having portions of their outer ends integral with the peripheral ring 38, whereby the member 35 may be formed of a single sheet metal disk. Preferably members 35 are assembled with their blades substantiallyy in alignment (Fig. 8) whereby the turbine 34 is formed of extremely light material with its blades occupying nearly all of the cross-sectional area of the air duct, thus being adapted to provide a greater starting torque in response to the air blast.

The opposite end of shaft 29 which adj oins the burner tip 2 carries a suitable spacer 40 which engages the fuel receiver 41. Preferably this fuel cup comprises a light shell 47 of resilient material, in the recommended form, being drawn or spun from sheet metal such as brass so that it is of eXtremely light weight. The shell may be frustoconical i-n form and is provided with a spider or annular portion 42 intermediate its ends but nearer its end of smaller diameter.

Member 42 comprises a disk of sheet metal with a struck up central boss 43 having an inturned flange 44 bolted upon a shoulder adjoining the end of shaft 29, Fig. 5, while a spacer 40 is located between the annular 'i member and the end of the bearing 29. The peripheral portion of member 42 has struck up castellations 45 that are spaced to provide grooves or longitudinal openings 46 adjoining the inner wall of shell 43. Preferigseigaie ably the castellations V45V are brazed or welded to the inner wall of the vcup and there-V after openings 49 are drilled in the annular member 42. Preferably cup 4l has an Vinturned flange 48 adjoining its small end in order to insure flow of oil through the grooves 46 and'openings 49, while a juxtaposed boss 65 upon spider 22 tends to exclude the main air draft from the interior of the cup, although permitting some air to be bled from the main air stream and to pass through openings 49, thus avoiding any tendency toward a vacuum adjoining flange 48, and providing an airflow of moderate intensity to carry fuel toward the open end of the cup.

The upstaiiding strut 50 of spider 21 is of somewhat larger cross section than the other struts in order to provide the oil well 5l. This oil Well is connected with the threaded elbow 52 which is jointed to the flexible fiiel line 53. The fuel pipe 54 within the air duct taps out of the lower portion of fuel well 5l and slopes downwardly through the .Y spider 22 terminating at a point adjoining the annular disk 42 within fuel receiver 41.-

annular groove 56 which is formed in thev outer surface of bearing sleeve 27, a suitable wick being disposed within the groove and being adapted to receive a small quantity of oil and to feed the same through the opening 59 to the bearing surface.

The upper longitudinal member 25 is tapped to receive the set screw 60 which engages the slotted portion 6I of conduit l in order to permit longitudinal adjustment of the frame 2O and the rotary means in relation to the conduit l and burner tip 2 to vary the type of flame emanating from the burner. Similarly an opening is made adjoining the elbow 52 to permit movement of that elbow in relation to the conduit l while the oil feed pipe is made flexible to permit the desired degree of movement between the burner cup and burner tip, or, if desired,

y pipe 53 may remain connected to frame 2O and the duct l may be movedlongitudinally after screw 60 has been loosened, thus effecting a similar adjustment between the nozzle and cup. Disconnection of elbow 52 and removal of screw 60 permits frame 25 and the rotary means carried thereby to be removed l as a unit and to be replaced, if so desired.

noz`zle2. Thus atomization of thefuelnoccurs and a suitable supply of airis received properly to support combustion. 'Ihe rotary means has a low moment of inertia since all parts thereof except the turbine unit and the fuel cup are confined to the immediate region o'f the shaft 29 which is of restricted diameter, while the turbine unit and fuel cup are formed of light'sheet metal. The

arrangement of the. frame 20 between the"- `turbine unit and cup permits the blades of the double turbine unit to occupy substantially the full cross-sectional area of the air conduit so that the initial action of the air blast causes a quick response of the rotaryvwl loads and low bearing speeds, even in conf" junction with high rotary speeds, which re- .sult from this design.

For example, in the illustrated einbodiment of the invention the diameter of the shaft does not exceed one-fourth the maxi`- mum dianietei of the fuel cup and preferably is less than a fifth of that diameter, Wliereby the bearing speed may be but a fraction of the speed of the cup portion which effects oil atomization. `Furthermore, the diversion of from the annular member 42 which is of the order of the diameter of that member. Since this self-supporting annular edge is relatively tliin the distortion of the same might readily occur in the assembly or subsequent handling of the fuel cup if the same were not resilient and thus not readily deformable. Use of a drawn brass shell for the rotary cup is extremely advantageous since it permits the utilization of thin sheet metal at a point where lightness is highly desirable; a cup of this character is resilient and forni-retaining, and thus, although very light, is not easily distorted from its proper form during assembly of the burner or during use. Furtherf more, the extremely lightconstruction of the fuel cup, in conjunction with the design of the frame which provides a greater resistance to the air blast adjoining the upper part of the conduit, results in a tendency of the rotary means to float in air. In other words, the air blast is of sufhcient intensity to provide a cushion of air under pressureto hold the rotary means in proper position, thus relieving the load upon theplain bearings. Acf

cordingly, an oily burner of this type utilizes simple, light, and inexpensive parts in order to provide a highly satisfactory and enduring construction which is highly efficient in use and is very responsive to the initial action Y of the air blast.

' bearings having a restricted internal diameter, said shaft being rotatably mounted in said bearings, said frame being longitudinally adjustable within the conduit, means f-or effecting said adjustment being located eXteriorly of the conduit and spaced from the nozzle end thereof to permit adjustment of the burner while combustion is occurring.

2. A burner comprising an air conduit, a fuel pipe within the conduit, rotary means arranged within the conduit, said rotary means including a shaftv of restricted diameter, a fuel-receiving cup secured thereto,

and a turbine mounted upon the shaft, a frame within the conduit having bearings of self-lubricating material, said shaft being mounted in the bearings, said cup comprising an outer sheet metal shell and an annular sheet metal portion connecting the shell to the shaft, said annular portion having fuel openings therein, and slots in the peripheral portion thereof.

3. A burner comprising an air conduit, a fuel passage within the conduit, rotary means arranged within the conduit, said rotary means including a shaft of restricted diameter, a fuel-receiving cup secured thereto, and a propeller mounted upon the shaft, a frame within the conduit having plain bearings, said shaft being mounted in the bearings, a fuel well Within the frame forming part of the fuel passage, a duct between said well and a bearing to divert a portion of the fuel for bearing lubrication.

'-i. A burner comprising an air conduit, a fuel passage, rotary means arranged within the conduit and including a light, fuel-receiving cup, a turbine carried at the end of said rotary means, and a shaft of restricted diameter connecting the turbine and cup, a frame within the conduit, plain bearings in the frame which support said. shaft, said frame being located between the turbine and cup, said cup comprising an outer shell of drawn sheet metal and an annular sheet metal portion connecting the shell with the shaft, the frame offering greater obstruction to the air blast in the region above the shaft, whereby the air blast tends to lift the light cup to relieve the load upon the adjoining bearing.

5. A fuel cup for oil burners comprising an outer shell of frusto-conical form, an inturned flange at the small end of said shell, an annular member within said shell spaced from its ends, but nearer to its end of smaller diameter, openings through said annular member, said shell being formed of drawn sheet metal, said annular member being formed of sheet metal with a struck-up peripheral portion secured to the shell.

6. A burner comprising an air conduit, a fuel pipe within the conduit, rotary means arranged within the conduit, said rotary means including a shaft, a fiiel-receiving cup secured thereto, and a propeller mounted upon the shaft, said cup comprising an outer sheet metal shell and an annular sheet metal portion securing the shell to the shaft, said annular portion having fuel openings therein, and slots in the peripheral portion thereof outwardly of said openings, lsaid annular portion having struck-up castellations upon its periphery to provide the slots adjoining the wall of the shell.

7. A burner comprising an air conduit, rotary means arranged within the conduit, said rotary means including a shaft and a fuel receiving cup, a frame supporting the portion of said shaft adjoining said cup, the cup comjrising an outer shell and an annular portion connecting the shell to the shaft, openings in said annular portion, an inturiied lip upon the end of said shell next to said frame, a boss upon the frame closely spacedfrom the lip, a fuel duct extending through said boss and terminating between the lip and shell, whereby a portion of the air passing through the conduit may enter the space between the boss and lip and aid the movement of fuel through the openings in the annular portion of the cup.

8. A burner comprising an air conduit terminating in a nozzle, a fuel passage, rotary means arranged within the conduit, a sheet metal fuel receiving cup at the end of the rotary means adjoining the nozzle, a sheet metal turbine at the opposite end of the rotary means, a shaft of restricted diameter connecting the turbine and cup, a frame within the conduit supporting said shaft, said frame being located between the cup and turbine and forming substantially the sole fixed obstruction to air flow within the conduit in the region of the turbine, said fuel passage entering the conduit between the turbine and cup, the turbine being secured to the shaft by fastening means which is restricted substantially to the region of the shaft, said turbine having blades occupying substantially all of the cross-sectional area of the conduit outside of said fastening means, whereby the turbine may receive substantially the full effect of the unobstructed air blast and the rotary means may be highly responsive to the same.

9. A burner comprising an air conduit terminating in a nozzle, rotary means arranged within the conduit, said means including a shaft, a fuel receiving cup secured thereto, and a turbine mounted thereon, a frame within the conduit having bearings supporting said shaft, a fuel-supplying passage connected to said frame, said frame being longitudinally slidable in the conduit to permit change in shape of the burner flame, holding means spaced from the nozzie and accessible from the outside of the conduit, said holding means being normally operable for holding the frame in any of its adjusted positions, the connection to the fuel-supplying passage permitting the ready movement of the frame, whereby the frame may be readily adjusted while combustion is occurring to permit immediate observation of the resulting change in the shape of flame.

10. Liquid fuel burning apparatus of the class described, comprising an air conduit, a burner tip portion at the end of the conduit having an open end through which air is forced, rotary means within said tip arranged to prepare the fuel for rapid combustion, said means comprising a skeleton frame arranged to be adjusted longitudinally of said tip, a shaft mounted in said frame and having an air actuated propeller fast thereto at the end removed from said open end, and a spider like support at its other end, an open ended cone shaped fuel receiver fast to said support, said support being located intermediate the ends of said receiver whereby an unobstructed portion of said receiver is arranged to receive the fuel, and an unobstructed portion thereof is arranged for preparing and discharging the fuel, said support having grooves in its periphery arranged to accelerate the speed of the fuel in its movement from the receiving portion to the preparing and discharging portion.

1l. Liquid fuel burning apparatus of the class described, comprising an air conduit, a burner tip portion at the end of the conduit having an open end through which air is forced, rotary means within said tip arranged to prepare fuel for rapid combustion, said means including a skeleton frame comprising two spaced spider like end members connected by two diametrically opposed struts, a shaft mounted in said members, an air actuated propeller secured to one end of said shaft, a! spider like support spaced from the end member adjacent said open end and secured to said shaft at the other end thereof, a conical open ended fuel receiving and discharging member fast to said support which is positioned intermediate the ends of said conical member whereby an unobstructed fuel receiving portion, and an unobstructed fuel preparing and discharging portion of greater capacity than said receiving portion are provided, one each side of said support, and means to adjust said rotarymeans longitudinally of said tip portionforthe purpose of controlling theshape of the flame.

12. A burner comprising an air conduit terminating in a nozzle, a fuelvpassage, rotary means arranged within the conduit, a fuel receiving cup `at the end of the rotary means adjoining the nozzle, a turbine at the opposite end of the rotary means, a solid shaft of restricted diameter connecting the turbine and cup, a frame within the conduit supporting said shaft., said frame being located between the cup and turbine and forming substantially `the sole Xed obstruction Y to air flow within the conduit in the region of the turbine, said fuel passage entering the conduit between the turbine and cup, the

turbine being spaced from the frame, the

latter having bearing receiving portions restricted to the vicinity of the sha-ft and having radial extensions extending outwardly to the inner face of the conduit wall to hold said bearing receiving port-ions in place, thereby minimizing the effect of back pressure on the turbine due to the impingement of airI upon the frame, said turbine having vblades occupying substantially all of the cross sectional area of the conduit outwardly of the restricted bearing receiving portions of the frame whereby the turbine may receive substantially the full effect of the unobstructed air blast and the rotary means may be highly responsive to the same.

13. A burner comprising an air conduit, a fuel pipe within the conduit, said conduit terminating in a nozzle portion, rotary means arranged within the conduit and including a shaft of restricted diameter, a fuel receiving cup secured to the shaft and disposed within the nozzle, and a turbine mounted upon the shaft, a frame within the conduit having a bearing of self-lubricating metal, said frame being disposed between the cup and turbine, the shaft being mounted in said bearing, said turbine and cup being secured to the shaft by fastening elements which are restricted to the immediate vicinity of the shaft, said turbine having blades which occupy nearly all of the cross-sectional area of the conduit outwardly of the corresponding fastening element, said cup and turbine being formed of sheet metal whereby the rotary means has a low moment of inertia and is readily responsive to the initiation of an air blast in the conduit.

lll. A burner comprising an air conduit to receive an intense air blast, said conduit terminating in a nozzle-like portion, a fuel f.

passage, rotary means arranged within the conduit and including a fuel-receiving cup at one end and disposed within the nozzle, a

turbine carried at the opposite end of said rotary means and a shaft of restricted diameter Connecting' the turbine and cup, a frame Within the conduit betWeen the turbine and cup, plain bearings in the frame supporting said shaft, said cup Comprising an outer shell having a self-supporting annular edge, said shell being drawn from thin sheet metal and being resilient, and means clamping the shell to the shaft and clamping the turbine to the shaft, said clamping means being confined to the immediate region of the shaft, whereby the rotary means may be highly responsive to the initiation of the air blast.

Signed by Ine at Lynn, Mass., this 9th day of August, 1927.

SINIUS M. HANSEN. 

